Battery management system

ABSTRACT

The present disclosure relates to a reconfigurable battery system and method of operating the same. The reconfigurable battery system comprising a plurality of switchable battery modules, a battery supervisory circuit, and a battery pack controller, where the plurality of switchable battery modules electrically arranged in series to define a battery string defining an output voltage. The battery pack controller operable to connect the battery string to the external bus via a pre-charge switch to perform a pre-charge cycle.

RELATED APPLICATION

This patent arises from a continuation of U.S. patent application Ser. No. 16/283,057, (now U.S. Pat. No. 11,108,251) which was filed on Feb. 22, 2019. U.S. patent application Ser. No. 16/283,057 is hereby incorporated herein by reference in its entirety. Priority to U.S. patent application Ser. No. 16/283,057 is hereby claimed.

FIELD

The present disclosure relates to battery power systems and methods, such as those suitable for use with aircraft.

BACKGROUND

The concept of high-altitude, long-endurance, solar-powered aircraft has been demonstrated by a number of aerial vehicle research projects. Solar power systems typically rely on an array of solar panels that interface with a battery grid (or similar battery systems) through control circuitry, such as a maximum power point (MPP) tracker.

An MPP tracker provides a circuit assembly that, in operation, adjusts the load impedance presented to the array of solar panels to achieve a maximum power out of the solar array. The power collected out of the solar array is then stored to the battery packs/assemblies of the battery grid. A maximum power point (MPP) tracker and other battery power systems, however, introduce additional weight and complexity to the overall system.

A need exists for solar and battery power systems and methods that can overcome the deficiencies of the prior art. Such a lightweight, efficient battery packs and battery pack assemblies may be employed with ultralight aircraft applications, such as long endurance solar-powered aircraft.

SUMMARY

The present disclosure relates to battery power systems and methods, such as those suitable for use with aircraft.

According to a first aspect, a method is provided for reconfiguring a battery system having a battery pack controller operably coupled to a plurality of switchable battery modules that are electrically arranged in series to define a battery string defining an output voltage, each of the plurality of switchable battery modules comprising a battery and a battery switch associated therewith, each battery switch configured to selectively connect its battery to the battery string or bypass its battery from the battery string, the method comprising: controlling a main switch to disconnect the battery string from an external bus; monitoring an amount of current passing through the battery string; once the amount of current is less than a predetermined current value, configuring, for each of the plurality of switchable battery modules, the battery switch in either a first position or a second position via the battery pack controller in accordance with a predetermined switching routine such that the output voltage is substantially equal to a predetermined target output voltage, wherein configuring the battery switch in the first position electrically places the battery in series with the battery string to increase the output voltage, and wherein configuring the battery switch in the second position electrically bypasses the battery from the battery string; connecting the battery string to the external bus via a pre-charge switch to perform a pre-charge cycle, wherein the pre-charge switch is operatively coupled in series with a resistor to limit current flow through the pre-charge switch; and once the pre-charge cycle is complete, controlling the main switch to connect the battery string to the external bus to perform a charge cycle.

In certain aspects, the step of monitoring the amount of current comprises: measuring the amount of current passing through the battery string; and comparing the amount of current to the predetermined current value to determine whether the amount of current is less than the predetermined current value.

In certain aspects, the method further comprises the step of outputting an error signal if the amount of current is greater than or equal to the predetermined current value and a predetermined period of time has passed.

In certain aspects, the steps of (a) measuring the amount of current and (b) comparing the amount of current are repeated if the amount of current is greater than or equal to the predetermined current value and a predetermined period of time has not passed.

In certain aspects, the pre-charge cycle comprises the steps of: determining a bus voltage at the external bus; determining the output voltage of the battery string; calculating a voltage difference (ΔV) between the bus voltage and output voltage; and determining whether the voltage difference (ΔV) meets one or more fault conditions, wherein the pre-charge cycle is complete if the voltage difference (ΔV) does not meet the one or more fault conditions.

In certain aspects, the one or more fault conditions are met if (A) the voltage difference (ΔV) is greater than a first predetermined voltage and (B) (1) a rate of change of the voltage difference (ΔV) is greater than a second predetermined voltage or (2) the voltage difference (ΔV) is greater than a third predetermined voltage.

In certain aspects, the first predetermined voltage is between 5 volts and 15 volts.

In certain aspects, the second predetermined voltage is between 2 volts and 8 volts.

In certain aspects, the third predetermined voltage is between 50 volts and 150 volts.

In certain aspects, if the one or more fault conditions are met and a predetermined period of time has not passed, the battery pack controller is configured to repeat the steps of: determining the bus voltage at the external bus; determining the output voltage of the battery string; calculating an updated voltage difference (ΔV) between the bus voltage and output voltage; and determining whether the updated voltage difference (ΔV) meets the one or more fault conditions.

According to a second aspect, a reconfigurable battery system comprises: a plurality of switchable battery modules electrically arranged in series to define a battery string defining an output voltage, each of the plurality of switchable battery modules comprising a battery and a battery switch, wherein the battery string is configured to electrically couple with an external bus via a main switch or a pre-charge switch; a battery pack controller to selectively switch, for each of the plurality of switchable battery modules, the battery switch between a first position that electrically places the battery in series with the battery string and a second position that electrically bypasses the battery from the battery string, wherein the battery pack controller is configured to perform the steps of: disconnecting the battery string from the external bus via the main switch; monitoring an amount of current passing through the battery string; once the amount of current is less than a predetermined current value, configuring, for each of the plurality of switchable battery modules, the battery switch in either the first position or the second position via the battery pack controller in accordance with a predetermined switching routine such that the output voltage is substantially equal to a predetermined target output voltage; connecting the battery string to the external bus via a pre-charge switch to perform a pre-charge cycle, wherein the pre-charge switch is operatively coupled in series with a resistor to limit current flow through the pre-charge switch; and once the pre-charge cycle is complete, controlling the main switch to connect the battery string to the external bus to perform a charge cycle.

In certain aspects, the step of monitoring the amount of current comprises: measuring the amount of current passing through the battery string; and comparing the amount of current to the predetermined current value to determine whether the amount of current is less than the predetermined current value.

In certain aspects, the battery pack controller is configured to output an error signal if the amount of current is greater than or equal to the predetermined current value and a predetermined period of time has passed.

In certain aspects, the steps of (a) measuring the amount of current and (b) comparing the amount of current are repeated if the amount of current is greater than or equal to the predetermined current value and a predetermined period of time has not passed.

In certain aspects, the pre-charge cycle comprises the steps of: determining a bus voltage at the external bus; determining the output voltage of the battery string; calculating a voltage difference (ΔV) between the bus voltage and output voltage; and determining whether the voltage difference (ΔV) meets one or more fault conditions, wherein the pre-charge cycle is complete if the voltage difference (ΔV) does not meet the one or more fault conditions.

In certain aspects, the one or more fault conditions are met if (A) the voltage difference (ΔV) is greater than a first predetermined voltage, and (B) (1) a rate of change of the voltage difference (ΔV) is greater than a second predetermined voltage or (2) the voltage difference (ΔV) is greater than a predetermined percentage more than a third estimated voltage drop over the resistor.

In certain aspects, if the one or more fault conditions are met and a predetermined period of time has not passed, the battery pack controller is configured to repeat the steps of: determining the bus voltage at the external bus; determining the output voltage of the battery string; calculating an updated voltage difference (ΔV) between the bus voltage and output voltage; and determining whether the updated voltage difference (ΔV) meets the one or more fault conditions.

In certain aspects, the battery switch of each of the plurality of switchable battery modules is a solid-state switch.

In certain aspects, the solid-state switch is a metal-oxide-semiconductor field-effect transistor (MOSFET) or an insulated-gate bipolar transistor (IGBT).

In certain aspects, the battery switch of each of the plurality of switchable battery modules is configured in a break-before-make (BBM) arrangement.

DRAWINGS

The foregoing and other objects, features, and advantages of the devices, systems, and methods described herein will be apparent from the following description of particular embodiments thereof, as illustrated in the accompanying figures; where like reference numbers refer to like structures. The figures are not necessarily to scale, emphasis instead being placed upon illustrating the principles of the devices, systems, and methods described herein.

FIG. 1 a illustrates an example solar-powered aircraft in accordance with a first aspect.

FIG. 1 b illustrates an example solar-powered aircraft in accordance with a second aspect.

FIG. 2 illustrates an example solar power system having a battery array.

FIG. 3 illustrates an example simplified single power channel for a solar-powered aircraft.

FIG. 4 illustrates a set of charts illustrating a maximum power point.

FIG. 5 illustrates an example electrical power system for the solar-powered aircraft.

FIG. 6 illustrates an example power diagram for an array consolidation and switching unit (ACSU).

FIG. 7 a illustrates a block diagram of a battery management system.

FIG. 7 b illustrates a block diagram of an example battery pack of a battery management system.

FIG. 7 c illustrates a diagram of an example battery string of a battery pack.

FIG. 8 a illustrates an example control method for reconfiguring a battery cell array.

FIG. 8 b illustrates an example method for monitoring the battery current through the battery string.

FIG. 8 c illustrates an example method for monitoring the battery voltage.

DESCRIPTION

References to items in the singular should be understood to include items in the plural, and vice versa, unless explicitly stated otherwise or clear from the text. Grammatical conjunctions are intended to express any and all disjunctive and conjunctive combinations of conjoined clauses, sentences, words, and the like, unless otherwise stated or clear from the context. Recitation of ranges of values herein are not intended to be limiting, referring instead individually to any and all values falling within the range, unless otherwise indicated herein, and each separate value within such a range is incorporated into the specification as if it were individually recited herein. In the following description, it is understood that terms such as “first,” “second,” “top,” “bottom,” “side,” “front,” “back,” and the like are words of convenience and are not to be construed as limiting terms.

As used herein, the terms “about,” “approximately,” “substantially,” or the like, when accompanying a numerical value, are to be construed as indicating a deviation as would be appreciated by one of ordinary skill in the art to operate satisfactorily for an intended purpose. Ranges of values and/or numeric values are provided herein as examples only, and do not constitute a limitation on the scope of the described embodiments. The use of any and all examples, or exemplary language (“e.g.,” “such as,” or the like) provided herein, is intended merely to better illuminate the embodiments and does not pose a limitation on the scope of the embodiments. The terms “e.g.,” and “for example” set off lists of one or more non-limiting examples, instances, or illustrations. No language in the specification should be construed as indicating any unclaimed element as essential to the practice of the embodiments.

As used herein, the terms “circuits” and “circuitry” refer to physical electronic components (i.e., hardware) and any software and/or firmware (“code”), which may configure the hardware, be executed by the hardware, and or otherwise be associated with the hardware. As used herein, for example, a particular processor and memory may comprise a first “circuit” when executing a first one or more lines of code and may comprise a second “circuit” when executing a second one or more lines of code.

As used herein, the terms “aerial vehicle” and “aircraft” are used interchangeably and refer to a machine capable of flight, including, but not limited to, both traditional runway and vertical takeoff and landing (“VTOL”) aircraft, and also including both manned and unmanned aerial vehicles (“UAV”). VTOL aircraft may include fixed-wing aircraft (e.g., Harrier jets), rotorcraft (e.g., helicopters, multirotor, etc.), and/or tilt-rotor/tilt-wing aircraft.

As used herein, the term “and/or” means any one or more of the items in the list joined by “and/or.” As an example, “x and/or y” means any element of the three-element set {(x), (y), (x, y)}. In other words, “x and/or y” means “one or both of x and y”. As another example, “x, y, and/or z” means any element of the seven-element set {(x), (y), (z), (x, y), (x, z), (y, z), (x, y, z)}. In other words, “x, y, and/or z” means “one or more of x, y, and z.”

As used herein, the term “composite material” as used herein, refers to a material comprising an additive material and a matrix material. For example, a composite material may comprise a fibrous additive material (e.g., fiberglass, glass fiber (“GF”), carbon fiber (“CF”), aramid/para-aramid synthetic fibers, etc.) and a matrix material (e.g., epoxies, polyimides, and alumina, including, without limitation, thermoplastic, polyester resin, polycarbonate thermoplastic, casting resin, polymer resin, acrylic, chemical resin). In certain aspects, the composite material may employ a metal, such as aluminum and titanium, to produce fiber metal laminate (FML) and glass laminate aluminum reinforced epoxy (GLARE). Further, composite materials may include hybrid composite materials, which are achieved via the addition of some complementary materials (e.g., two or more fiber materials) to the basic fiber/epoxy matrix.

As used herein, the term “composite laminates” as used herein, refers to a type of composite material assembled from layers (i.e., a “ply”) of additive material and a matrix material.

As used herein, the terms “communicate” and “communicating” refer to (1) transmitting, or otherwise conveying, data from a source to a destination, and/or (2) delivering data to a communications medium, system, channel, network, device, wire, cable, fiber, circuit, and/or link to be conveyed to a destination.

As used herein, the term “processor” means processing devices, apparatuses, programs, circuits, components, systems, and subsystems, whether implemented in hardware, tangibly embodied software, or both, and whether or not it is programmable. The term “processor” as used herein includes, but is not limited to, one or more computing devices, hardwired circuits, signal-modifying devices and systems, devices and machines for controlling systems, central processing units, programmable devices and systems, field-programmable gate arrays, application-specific integrated circuits, systems on a chip, systems comprising discrete elements and/or circuits, state machines, virtual machines, data processors, processing facilities, and combinations of any of the foregoing. The processor may be, for example, any type of general purpose microprocessor or microcontroller, a digital signal processing (DSP) processor, an application-specific integrated circuit (ASIC). The processor may be coupled to, or integrated with a memory device. The memory device can be any suitable type of computer memory or any other type of electronic storage medium, such as, for example, read-only memory (ROM), random access memory (RAM), cache memory, compact disc read-only memory (CDROM), electro-optical memory, magneto-optical memory, programmable read-only memory (PROM), erasable programmable read-only memory (EPROM), electrically-erasable programmable read-only memory (EEPROM), a computer-readable medium, or the like.

As used herein, the term “solar panel” refers to an array of one or more photovoltaic cells configured to collect solar energy to generate electrical power. The solar panels may employ one or more of the following solar cell types: monocrystalline silicon solar cells, polycrystalline silicon solar cells, string ribbon solar cells, thin-film solar cells (TFSC), cadmium telluride (CdTe) solar cells, copper indium gallium selenide (CIS/CIGS) solar cells, and the like. To reduce overall weight and to improve reliability and durability, it is advantageous to employ light weight and/or flexible solar panels (e.g., thin-film solar panels).

As used herein, circuitry or a device is “operable” to perform a function whenever the circuitry or device comprises the necessary hardware and code (if any is necessary) to perform the function, regardless of whether performance of the function is disabled, or not enabled (e.g., by a user-configurable setting, factory trim, etc.).

FIGS. 1 a and 1 b illustrate example solar-powered aircraft 100 a, 100 b. Specifically, FIG. 1 a illustrates an isometric view of a first solar-powered aircraft 100 a with a single fuselage 110 and tail boom 104, while FIG. 1 b illustrates an isometric view of a second solar-powered aircraft 100 b with a set of two side-by-side fuselages 110 a, 110 b and a set of two side-by-side first and second tail booms 104 a, 104 b. As illustrated, each of the two side-by-side fuselages 110 a, 110 b may include a propulsor 124. The solar-powered aircraft 100 a, 100 b generally comprises a wing 102, one or more propulsors 124 (e.g., a propeller 124 a and associated gearing, which is axially driven by one or more motors 124 b), one or more fuselages 110 (e.g., a single fuselage 110 or a set of fuselages 110 a, 110 b), one or more tail booms 104 (e.g., a single tail boom 104 or a set of tail booms 104 a, 104 b; each illustrated as an elongated boom coupled to the aft end of a fuselage 110), one or more tail sections 112 (e.g., a single tail section 112 or a set of tail sections 112 a, 112 b), and landing gear 120. As illustrated, the wing 102 comprises a first wing tip 122 a (port side), a second wing tip 122 b (starboard side), and a midpoint 122 c along the wing's 102 wingspan that is approximately half way between the first wing tip 122 a and the second wing tip 122 b.

The various structural components of the solar-powered aircraft 100 a, 100 b may be fabricated from metal, a composite material, or a combination thereof. For example, portions of the wing 102 may be fabricated using fused deposition modeling (FDM), stereolithography (SLA), selective laser sintering (SLS), and/or any other suitable type of additive manufacturing/3D printing. A benefit of this fabrication method is that it produces a high-performing, more stable aircraft, using advanced sensing and 3D printing disciplines. FDM is a thermal polymer layer deposition process that produces components one layer at a time, effectively printing aircraft components rapidly, in low-volume, and to exacting material specifications. Using FDM, numerous wing design iterations may be inexpensively manufactured to meet desired strength and stiffness requirements, control surface sizing, and other characteristics. Further, additional wing panels/components may be fabricated to allow for tailored sensor integration, ease of generating additional actuation schemes or altering the control surface placement, ease of characterizing the strain on the wing, and an ability to easily alter the wing's stiffness to provide the best platform for proprioceptive sensing in a given application. This capability also offers robustness against wing damage, as replacement components are readily reproducible.

Each propulsor 124 generally comprises a motor 124 b coupled to, and configured to drive/rotate, a propeller 124 a. The motor 124 b may be an electric motor controlled via a motor controller 306, such as an electronic speed controller (ESC) unit. To that end, an ESC unit (or another motor controller 306) may be provided to control the motor 124 b, which may be coupled (or otherwise integrated) with the wing 102 (e.g., as part of a nacelle pod). The propulsor 124 may be positioned on the wing 102, the tail boom 104 (e.g., at the proximal end), or a combination thereof. For example, each of the propulsors 124 may be positioned on, or within, the wing 102 in either a pusher configuration or a tractor configuration (as illustrated). Further, while each fuselage 110 is illustrated as having a single propulsor 124 associated therewith, additional propulsors 124 may be provided. Regardless of the propulsion configuration, each of the plurality of propulsors 124 may be oriented to direct thrust toward the distal end of the tail boom 104 (aft).

The wing 102 and/or the horizontal stabilizer 126 may comprise one or more arrays of solar panels 106 to generate power. As illustrated in FIG. 1 a , the solar panels 106 may be positioned on each side of the tail boom 104/fuselage 110 along the upper surface of the wing 102. The solar-powered aircraft 100 a, 100 b may further comprise one or more energy storage devices operatively coupled to the solar panels 106 to power the vehicle management system 218 and various electric loads. The one or more energy storage devices store collected solar energy for later use by the solar-powered aircraft 100 a, 100 b (e.g., when sunlight is unavailable, typically at nighttime). As used herein “energy storage device” refers to a battery or similar instrumentality known to those of skill in the art capable of storing and transmitting energy collected from the solar panels 106, including but not limited to a rechargeable battery (e.g., lithium-polymer batteries), a regenerative fuel cell, or combinations thereof.

While the wing 102 is illustrated as generally linear with non-tapered outboard portions, other configurations are contemplated, such as back-swept, tapered, rectangular, elliptical, forward-swept, and the like. Therefore, the wing 102 may be any type of fixed wing, including, but not limited to, a straight wing, a swept wing, a forward-swept wing, a dihedral wing (an upward angle from horizontal), an anhedral wing (a negative dihedral angle—downward angle from horizontal), or any other suitable type of fixed wing as known by those of ordinary skill in the art. As illustrated, the wingspan of the wing 102 may be substantially perpendicular relative to the longitudinal length of the fuselage(s) 110 and tail boom(s) 104; however, the wing 102 may instead be swept back or swept forward. In certain aspects, the wing 102 may be modular and configured for disassembly; thereby allowing the solar-powered aircraft 100 a, 100 b to be more easily transported by land and/or to physically fit within a hanger or other structure for storage. For example, the wing 102 may be fabricated from a plurality of wing panel modules and removably joined to one another end-to-end via a set of joints. Each of the joints may employ one or more fasteners (e.g., bolts, clips, etc.) and electrical connectors (e.g., plugs, contacts, etc.) to facilitate both physical and electrical coupling therebetween.

As can be appreciated, control surfaces on the wing typically require additional structural reinforcements and actuators, which result in additional weight. In addition, adding control surfaces to a wing increases the drag during flight. Further, control surfaces on a wing can also require that the skin panel be broken into sections, as opposed to having a substantially unbroken construction that allows for the solar panels 106 to cover more of the upper surface of the wing 102. Finally, manufacturing control surfaces adds complexity as attachment mechanisms, hinges, additional parts, and/or multiple skin panels must be made. Removing the control surfaces, however, eliminates these complexities. Therefore, unlike traditional aircraft, the wing 102 need not include movable control surfaces (e.g., flaps, slats, etc.) along the trailing or leading edges of its wingspan. Indeed, to reduce weight and complexity, the wing 102 may be generally devoid of movable control surfaces. For example, the upper and lower surface of the wing 102 may be fabricated as a single piece structure without any moving parts. Control of the wing 102 may instead be achieved through control surfaces positioned on one or more of the tail sections 112 positioned at the distal end of each tail boom 104.

The solar-powered aircraft 100 a, 100 b may employ one or more tail booms 104. In one aspect, a single tail boom 104 (see FIG. 1 a ) or in other aspects, multiple tail booms, for example, a first tail boom 104 a and a second tail boom 104 b (see FIG. 1 b ). Regardless of configuration, each tail boom 104 defines a proximal end and a distal end, where each of the tail booms 104 may be secured at its proximal end to a fuselage 110 or a wing 102, while being coupled to a tail section 112 at its distal end. The solar-powered aircraft 100 a, 100 b (e.g., the tail booms 104, fuselages 110, etc.) may be fabricated using a tubular core structure 118, which may then be covered with aircraft skin (e.g., composite materials, fabric, metal, metals alloys, etc.). Detail A of FIG. 1 a best illustrates the tubular core structure 118, where the aircraft skin has been removed for clarity. In certain aspects, the tail boom 104 and the fuselage 110 may be fabricated as a single, unitary component. While the solar-powered aircraft 100 b is illustrated as having two fuselages 110 and two tail booms 104, a person of skill in the art would understand that additional, or fewer, fuselages 110/tail booms 104 may be employed to achieve a desired function and as a function of, for example, the length of the wing 102.

To facilitate takeoff and landing, the solar-powered aircraft 100 a, 100 b may be provided with one or more sets of landing gear 120, which may be positioned on the undercarriage of the aerial vehicle. For example, a set of landing gear 120 may be provided at the underside of the wing 102, fuselage 110, and/or tail boom 104. The landing gear 120 may employ, inter alia, a set of wheels (as illustrated) and/or skids. In operation, the landing gear 120 serves to support the solar-powered aircraft 100 a, 100 b when it is not flying; thereby allowing it to take off, land, and taxi without causing damage to the airframe.

As illustrated, each tail section 112 may comprise one or more one control surfaces to move/steer the tail section 112 in a desired direction. For example, each tail section 112 may comprise a vertical stabilizer 108 (e.g., a dorsal fin) extending vertically (above and/or below) from the tail boom 104, a rudder 114 operatively coupled to the vertical stabilizer 108, a horizontal stabilizer 126 extending laterally from either side of the tail boom 104, and an elevator 116 (or portion thereof) operatively coupled to each side of the horizontal stabilizer 126. The tail sections 112 of the solar-powered aircraft 100 a, 100 b may be selectively controlled (e.g., via a flight controller/vehicle management system 218) to control the overall pitch, roll, and yaw of the solar-powered aircraft 100 a, 100 b, thereby obviating the need for movable control surface on the wing 102. The elevators 116 may be used to change the pitch of the tail section 112, while the rudder 114 may be used to change the yaw of the tail section 112. The pitch and/or yaw of the tail sections 112 may be separately controlled via the rudders 114 and/or elevators 116 to create a local force moment at the location the tail boom 104 attaches to the wing 102.

Each rudder 114 may be rotatably and/or hingedly coupled to a vertical stabilizer 108 via one or more hinges to enable the rudder 114 to move about an axis defined by the vertical stabilizer 108 at its trailing edge. Similarly, the elevators 116 may be rotatably and/or hingedly coupled to the horizontal stabilizer 126 via one or more hinges to enable movement about an axis defined by the horizontal stabilizer 126 at its trailing edge. In certain aspects, one or more of the rudders 114 and/or the elevators 116 may additionally be configured with a mechanism (e.g., rails, tracks, etc.) to allow for other, non-rotatable movement, such as, for example, sliding and/or lateral movement relative to the vertical or horizontal stabilizer. In alternative embodiments, one or more of the rudders 114 and/or the elevators 116 may be omitted entirely from a given tail section 112. Depending on the desired tail configuration, the horizontal stabilizer 126 and vertical stabilizers 108 may be operatively coupled to one another as well as the tail booms 104, or operatively coupled only to the tail booms 104. The tail section 112 may be configured in one of multiple tail configurations, including, for example, fuselage mounted, a cruciform, T-tail, a flying tailplane, a pi-tail (i.e., it-tail), a V configuration, an inverted V configuration (i.e., “Λ” configuration), a twin tail (H-tail arrangement or U-tail arrangement), etc. Further, the horizontal stabilizer 126 may be straight, back-swept, tapered, rectangular, elliptical, forward-swept, etc. In certain aspects, the tail section 112 may employ a combination H- and Λ-tail arrangement where the tail section 112 comprises Λ-tail surfaces that couple to the horizontal stabilizer 126 to provide a combination H- and Λ-tail arrangement.

Persons of ordinary skill in the art will recognize that alternative and/or additional structural arrangements may be implemented to accommodate the design and/or operational requirements of the tail section 112. For example, the tail section 112 may instead employ only one or more vertical stabilizer 108, one or more horizontal stabilizer 126, and/or slanted or offset stabilizers that have both horizontal and vertical dimensions. Additionally, or alternatively, the tail section 112 may include multiple rudders 114 on the vertical stabilizer 108 and/or a plurality of elevators 116 on each side of the horizontal stabilizer 126.

The solar-powered aircraft 100 a, 100 b may employ a vehicle management system 218 operable to control the various functions of the solar-powered aircraft 100 a, 100 b. As illustrated in FIG. 2 , the solar-powered aircraft 100 a, 100 b may be equipped with one or more battery arrays 200 to supply power to the various electric loads 220. The electric load 220 may include, for example, one or more payloads (e.g., an intelligence surveillance reconnaissance (ISR) payload), one or more motors (e.g., the motors 124 b used in connection with the propulsors 124), actuators (e.g., to control the flight control surfaces of the tail section 112, landing gear 120, and the like), etc. Each battery array 200 generally comprises one or more battery banks 224, each battery bank 224 having a plurality of battery pack assemblies 202 electrically coupled to each other; thereby defining, along its longitudinal length, a power supply line 204, a ground line 206, and, where desirable, a data communication line 208. The ground line 206 may be electrically coupled to an equipotential point 222 (e.g., ground). As illustrated, the battery pack assemblies 202 within a battery bank 224 may be arranged electrically in parallel. The data communication line 208 may be shielded so as to mitigate electromagnetic interference (EMI) for, inter alia, the power supply line 204. The data communication line 208 may be coupled to one or more sensors or devices 214 that monitor or control, for example, the health and/or operating parameters (e.g., temperature, humidity, voltage, etc.) of each battery pack assembly 202 or battery pack 212.

The battery pack assemblies 202 within a battery bank 224 may be electrically connected to one another via one or more interconnectors 210 to facilitate the passing of power and/or data signals from one battery pack assembly 202 to another battery pack assembly 202 (e.g., an adjacent battery pack assembly 202). The interconnectors 210 may employ, for example, a first connector 210 a (e.g., a female connector) and a second connector 210 b (e.g., a male connector) configured to mate with one another. For example, when arranged in a row/string, power and/or data signals may be conveyed, or otherwise communicated, from one end (e.g., proximal end) of a battery array 200 to an opposite end (e.g., distal end) of the battery array 200 via the interconnectors 210; each of which can provide pass through functionality in the event of an isolated battery pack assembly 202 failure. For instance, the battery pack assemblies 202 can integrate the power rails (e.g., power supply line 204, ground line 206) and data communication lines 208 with in-line connections such that battery pack assemblies 202 can be attached to one another to form continuous power and data pathways for feeding the load and interacting with the system controller 216. Each of the battery pack assemblies 202 may be selectively switched online (connected) to or switched offline (disconnected) from the battery bank 224 via one or more switching units 228 (e.g., relays, solid-state switches, etc.). For example, in the event of failure/malfunction or to achieve a desired power/capacity.

In certain aspects, a battery bank 224 within the battery array 200 can be expanded and contracted as needed (e.g., additional battery pack assemblies 202 may be connected or disconnected). In other words, power and/or data signals are carried across the battery bank 224, thereby only requiring an electrical connection at one end of the battery bank 224. Consequently, an energy storage system having such battery banks 224 provide for quick electrical and mechanical integration. Further, the battery pack assemblies 202 may be fabricated in bulk, thereby obviating the need for costly, complicated, and potentially unreliable harnesses. In operation, the system controller 216, which may be processor-controlled, monitors each of the one or more battery arrays 200 (and separately, each battery bank 224, battery pack assembly 202, or battery cells 772), the one or more solar panels 106 (e.g., a solar array 226 composed of at least two solar panels 106), and the one or more electric loads 220. For instance, in response to an input parameter (e.g., an instruction from the solar-powered aircraft's 100 vehicle management system 218), the system controller 216 may adjust the electric load 220 and/or adjust (or reallocate) power from the one or more battery arrays 200 to meet the electric load's 220 needs. To that end, the system controller 216 may incorporate, or be operatively coupled with, a plurality of battery pack controllers. The system controller 216 may communicate through either a simplex or redundant communications bus to each of the battery pack assemblies 202 in an energy storage system (e.g., battery array 200 or battery bank 224). The system controller 216 may employ one or more control area network (CAN) buses for monitoring, communication, and/or control, while an external bus may be used to transfer power between the battery bank(s) 224 (or components thereof) and the electric load 220 or solar array 226. In certain aspects, as will be discussed below, the battery array 200 may employ a power allocation switching unit system and/or algorithm for managing battery groups and solar panels, such as an array consolidation and switching unit (ACSU).

The battery array 200, whether composed of a single battery bank 224 or multiple battery banks 224, offers a number of features and advantages. First, the battery array 200 stores electrical power for the electric loads 220. By way of illustration, the solar-powered aircraft's 100 battery arrays 200 may provide, in aggregate, about 50 to 100 kWh in total energy storage to the solar-powered aircraft 100 a, 100 b when fully charged. As can be appreciated, however, the amount of energy storage can be increased or decreased by adjusting the number of battery pack assemblies 202 to achieve a desired amount of energy storage. Second, the battery array 200 supplies power through nighttime operation for at least a predetermined period of time (e.g., about 60 to 120 days, or about 90 days). Finally, the battery array 200 tolerates single-fault for flight safety such that the battery array 200 will operate normally in the event of a failure of a battery pack assembly 202, a battery pack 212, or battery cell 772 thereof. For example, the components of the battery array 200 can be provided as line replaceable units (LRU), where a defective battery cell 772 in the battery pack 212 can be switched offline (e.g., switched out/bypassed) to provide further fault protection. Similarly, a defective battery pack 212 in the battery pack assembly 202 can be switched offline to provide further fault protection. Each battery pack assembly 202 may contain, for example, six battery packs 212. The battery packs 212 may be arranged in series, parallel, or a combination thereof to yield a self-reconfigurable multi-cell system (e.g., configured to supply between 130 VDC and 327 VDC). As will be discussion in connection with FIGS. 7 a through 7 c , the battery cells 772 of the battery pack 212 may be dynamically reconfigured to enable, inter alia, solar peak power tracking and discharge voltage regulation.

FIG. 3 illustrates a diagram of an example simplified single power channel 300 for the solar-powered aircraft 100 a, 100 b. As will be appreciated, the solar-powered aircraft 100 a, 100 b may use multiple simplified single power channels 300 (e.g., one per fuselage 110, one per propulsor 124, etc.). The ACSU 302 may be operably coupled to the battery array 200 (or portion thereof) and the solar panels 106 (or a solar array 226). The AC SU 302 is used to distribute power with and/or between the battery array 200, the solar panels 106, and the electric loads 220 (e.g., the drive system 314, avionics 312, and any payloads). The drive system 314 generally comprises a motor controller 306, one or more propulsors 124 (e.g., a propeller 124 a coupled to a motor 124 b), and output filtering 320, which filters power delivered by the motor controller 306. The output filtering 320 (e.g., one or more electronic filters) may be positioned between the motor controller 306 and the one or more propulsors 124. The motor 124 b may employ, for example, an ironless core Halbach array. A Halbach array employs an arrangement of permanent magnets that augments the magnetic field on one side of the array, while cancelling the field to near zero on the other side. This is achieved by having a spatially rotating pattern of magnetization.

The propeller 124 a may employ variable pitch blades where the blades are configured to rotate about their long axis to change the blade pitch relative to the hub. In certain aspects, the propeller 124 a may be configured as a reversible propeller where the pitch can be set to a negative value, thereby creating a reverse thrust. A reverse thrust can be used for, inter alia, braking without the need to change the direction of shaft revolution. An optimal pitch for the propeller blade during climb flight conditions can be selected as a function of the motor's 124 b design or operating parameter. In certain aspects, the propeller blades may be pitched to maintain an amount of thrust while the RPM is decreased. For example, where the maximum velocity and minimum DC bus voltage define a motor voltage constant (KV), the ceiling climb velocity may be reduced from 1,100 to 1,000 revolutions per minute (RPM) to decrease velocity range and increase optimum DC bus voltage for cruise at altitude.

A motor controller 306 is an electronic circuit configured to vary a motor's speed, its direction, and, when desired, to act as a dynamic brake. The motor controller 306 is illustrated with a DC link 316 and a voltage-source inverter (VSI) converter 322, where the rectifier comprises a diode-bridge and the DC link 316 is a shunt capacitor. The motor controller 306, in effect, provides an electronically-generated three-phase electric power voltage source of energy for the motor 124 b. In operation, the motor controller 306 provides an electronically-generated three-phase electric power voltage source of energy for the motor 124 b. The pulse width modulation (PWM) frequency of the motor controller 306 may be optimized for combined motor 124 b and motor controller 306 efficiency. For example, the PWM frequency may be optimized to lower control risk due to high rate of current change (dI/dt), which can be particularly useful in situations with large voltage overhead. Further, optimizing the PWM frequency can address bus capacitance for short and long lines and bus outage.

The voltage at which a solar panel 106 or a solar array 226 can produce maximum power is called the maximum power point (MPP, or, sometimes, peak power voltage). With reference to the current (A) and power (kW) graphs 400 a, 400 b of FIG. 4 , MPP tracking (MPPT) is used to extract a maximum available power from the solar panel 106 at the current conditions. MPPT is important in solar powered systems. Generally, MPPT varies solar panel load loading to optimize solar output power. The electrical connection between solar panel(s) 106 and battery array 200 (or portion thereof), in conjunction with dynamic reconfiguration of the battery array 200, enables MPPT of the solar panel(s) 106 (e.g., at 2 Hz). For example, a perturb-and-observe algorithm may be applied as the MPPT control scheme. Perturb-and-observe techniques can be implemented by adding (or removing) a battery cell 772 to (or from) the battery pack 212. Therefore, in operation, battery cells 772, for example, can be added or removed from the battery string in battery pack 212 to facilitate MPPT. Generally, optimum voltage can be achieved within ½ cell voltage on average with only approximately ˜0.7% error.

During daylight hours, each solar panel 106 may be connected to a battery bank 224, whereby solar energy collected by the solar panels 106 is used to charge the battery bank(s) 224. Solar panels 106 that are generating the highest power (e.g., the most power) may further be used to supply power to the drive system 314, thereby maximizing usage of the generated power. As can be appreciated from the diagram, there is no power conversion loss between the solar panels 106 and battery bank 224/electric loads 220, aside from Joule loss attributable to, for example, wiring resistance and heating.

FIG. 5 illustrates a block diagram of an example electrical power system 500 for the solar-powered aircraft 100 a, 100 b. In operation, the electrical power system 500 provides power to the solar-powered aircraft 100 a, 100 b via a combination of battery arrays 200 and solar panels 106 (e.g., solar arrays 226). While the following discussion and figures will use the term solar panel 106, it should be understood that the disclosure is not necessarily limited to a single solar panel 106, but could be a single solar panel 106 or multiple solar panels 106 arranged in a solar array 226.

Power from the solar panel 106 and/or battery array 200 can be used to power, inter alia, avionics 312 (e.g., actuators, control systems, etc.), one or more payloads 504, etc. For example, the power from the solar panel 106 and/or battery array 200 may be used to power, in response to commands from a flight controller or the vehicle management system 218, one or more wing servos 308 a (e.g., actuators to control the flight control surfaces on the wing 102, if used, such as aileron) and tail servos 308 b (e.g., actuators to control the flight control surfaces on the tail sections 112, such as rudders 114 and elevators 116). The battery arrays 200 and various servos (e.g., the wing servos 308 a and the tail servos 308 b) may be monitored by a line replaceable unit (LRU) 310.

Each battery array 200 may include one or more battery pack assemblies 202, which may be arranged into one or more battery banks 224, each battery bank 224 being composed of two or more battery pack assemblies 202. The battery banks 224, for example, may be positioned on the fuselage 110, tail sections 112, the wing 102 (e.g., the leading edge or the upper surface), etc. Each propulsor 124 is illustrated as having a motor 124 b and a dedicated motor controller 306. Additional solar panels 106 may be positioned on each of the tail sections 112 (e.g., the horizontal stabilizer 126 and the vertical stabilizer 108). In certain aspects, the wing 102 may support multiple solar panels 106 that are arranged into different, separate solar arrays 226. For example, a first solar panel 106 may be positioned at the leading edge, while a second solar panel 106 may be positioned on an upper (top) surface of the wing 102, between the leading edge and the trailing edges (e.g., forward of flight control surfaces, if used).

An advantage of the electrical power system's 500 architecture is that the power buses are nominally isolated from one another. For example, the electrical power system 500 may be generally divided into sub-systems 502 a, 502 b, 502 c (e.g., electrically-isolated domains) such that electrical failure in one sub-system does not propagate to another sub-system. For example, the electrical power system 500 may be generally divided into two or more electrically isolated sub-systems (illustrated as three sub-systems 502 a, 502 b, 502 c in FIG. 5 ), each sub-system may correspond to a different region of the solar-powered aircraft 100 a, 100 b (e.g., a fuselage 110, wing 102, portion of a wing 102, etc.). Accordingly, damage to components of the electrical power system 500 situated at one region of the solar-power aircraft 100 a, 100 b (e.g., a wing 102) should not propagate to components of the electrical power system 500 situated at other regions of the solar-power aircraft 100 a, 100 b (e.g., the fuselages 110, tail sections 112, etc.). As illustrated, each sub-system 502 a, 502 b, 502 c of the solar-powered aircraft 100 a, 100 b may include a solar panel 106 to collect energy, a battery bank 224 to store energy collected by the solar panel 106, and a dedicated ACSU 302 a, 302 b, 302 c.

While sub-systems 502 a, 502 b, 502 c are self-sufficient to limit failure propagation, to further mitigate failures, cross-tie switches 304 a, 304 b can be positioned between sub-systems 502 a, 502 b, 502 c to transfer power across the solar-powered aircraft 100 a, 100 b. Therefore, the ACSUs 302 a, 302 c of the first and third sub-systems 502 a, 502 c may couple to the ACSU 302 b of the second sub-system 502 b via a set of cross-tie switches 304 a, 304 b. In operation, the cross-tie switches 304 a, 304 b may be selectively actuated to couple, electrically and communicatively, the desired sub-systems 502 a, 502 b, 502 c. For example, in the event of failure of the ACSU 302 c of the third sub-system 502 c, the cross-tie switch 304 b may be actuated to allow the ACSU 302 b of the second sub-system 502 b to control the power components of the third sub-system 502 c in lieu of the ACSU 302 c. The cross-tie switches 304 a, 304 b may employ mechanical switches (e.g., solenoid-driven relays), solid-state switches (e.g., transistors, such as insulated-gate bipolar transistors (IGBT), field effects transistors (FETs), metal-oxide-semiconductor field-effect transistors (MOSFET), etc.), or a combination thereof. Each of the cross-tie switches 304 a, 304 b may be controlled by, for example, one or more of the ACSUs 302.

FIG. 6 illustrates a power diagram 600 for an example ACSU 302. The ACSU 302, which is illustrated in the daytime configuration, provides flexibility in powering the motors 124 b coupled to a local motor bus 324 from one or more sources. As illustrated, the ACSU 302 is coupled to one or more solar panels 106 and battery banks 224, which may be positioned on the wing 102, tail section 112, etc. As illustrated, the battery banks 224 can be coupled to the local motor bus 324 through one or more of the ACSU 302 within the electrical power system 500. The number of battery pack assemblies 202 or battery banks 224 in each battery array 200 may vary depending on the physical constraints of the installation location in the solar-powered aircraft 100 a, 100 b. For example, five battery pack assemblies 202 may be arranged in a battery bank 224 in each wing 102, while two battery packs assemblies 202 may be arranged in a battery bank 224 of the leading edge of each wing 102 and/or the tail section 112. The battery banks 224 may be coupled to the local motor bus 324 using one or more switches 328 as a function of, inter alia, the charge state of the battery array 200 and/or maximum power points (MPP) voltage of the solar panel 106. The one or more switches 328 may be mechanical switches, solid-state switches, or a combination thereof. One or more electrical safety devices 326 (e.g., fuses, e-Fuses, circuit breakers, resettable fuses, such as a polymeric positive temperature coefficient (PPTC) devices, etc.) may be provided in-line between the local motor bus 324 and the motor controller 306 to provide over-current protection. While the solar panels 106 of FIG. 6 are illustrated as tied directly to a battery bank 224, the avionics 312 and/or payload 504 may instead be configured to pull power from all battery banks 224 of the electrical power system 500, which may be arranged in an “OR” configuration using, for example, ideal diodes.

Solar panels 106 can display different MPP voltages depending on the age and operating conditions of the solar-powered aircraft 100 a, 100 b. Operating conditions include, for example, shadowing, incident angle, etc. Therefore, the solar-powered aircraft's 100 solar panels 106 are distributed as solar arrays 226 on areas of the airframe that have similar solar incidence angles (displaying similar power point behavior). By separating the electrical power system 500 into multiple sub-systems 502 a, 502 b, 502 c, each representing an array zone (e.g., an array zone for each of the fuselage, wing, leading edge, tail, etc.) and separately controlling the battery voltage in each zone, the MPP for each solar array 226 is achieved. The solar-powered aircraft 100 a, 100 b may have, for example, nine separate solar arrays 226, each corresponding to a different array zones. The array zones can include, for each wing 102 (or portion thereof), a leading edge array, a wing (upper surface) array, and a tail array.

Due to their surface area, the wing(s) 102 is/are typically the largest overall contributor to energy collection. The solar panels 106 may employ thin-film copper indium gallium selenide (CIGS) for the bulk of the solar arrays, which offer efficiencies of about 12 to 17%. Thin-film CIGS arrays can be fabricated on a flexible substrate, which is useful for covering curved surfaces (e.g., aircraft wings). The flexible substrate may be, for example, a polyamide substrate. In another aspect, where desired, the solar panels 106 may employ thin-film gallium arsenide (GaAs) to target high-value locations on the solar-powered aircraft 100 a, 100 b, which offer efficiencies in excess of 25%. During testing, GaAs arrays have demonstrated un-encapsulated efficiencies of about 28% with a mass of 237 g/m², which is about 2.6 times the mass of the CIGS arrays.

Traditional, rechargeable battery packs contain a hardwired string of batteries (a fixed battery string). A fixed battery string architecture can minimize the footprint (e.g., size, weight, power requirements, etc.) of the battery management system, but the output voltage has an increasing variance during a cycle from fully charged to fully discharged as the battery cell count increases and/or the battery cells cycle from fully charged to fully discharged. Therefore, as a result of the large output swing, additional hardware is typically implemented to regulate the output voltage of the battery system at a penalty of reduced overall efficiency lost to the output conversion process. A battery management system that can intelligently reconfigure the number of batteries (e.g., battery cells) in a battery string can obviate the need for an additional voltage regulator stage. Therefore, the battery array 200 may allow for dynamic reconfiguration at various levels of control granularity (e.g., per battery bank 224, per battery pack assembly 202, per battery pack 212, and/or per battery cell 772).

Battery pack assemblies 202 in each sub-system 502 a, 502 b, 502 c or region of the solar-powered aircraft 100 a, 100 b may be partitioned into battery banks 224. Each battery bank 224, as noted above, is typically composed of two or more battery pack assemblies 202. The quantity of battery pack assemblies 202 per battery bank 224 and the number of battery banks 224 per sub-system 502 a, 502 b, 502 c may be sized based on the size of the local solar panel 106 (or solar array 226) and contribution to overall energy collection. In one example, five battery pack assemblies 202 may be arranged to define the battery bank 224. Each battery bank 224 may be matched to a solar panel 106 or solar array 226. For example, (1) the solar panel 106 in the wing 102 may be paired with the battery bank 224 in the wing 102, (2) the solar panel 106 in the leading edge of the wing 102 may be paired with the battery bank 224 in the leading edge of the wing 102, and (3) the solar panel 106 in the tail section 112 may be paired with the battery bank 224 in the tail section 112. The matching may be designed to minimize the effect upon the electrical power system 500 in the event of localized damaged to the solar-powered aircraft 100 a, 100 b.

The solar-powered aircraft 100 a, 100 b can include a battery management system 700 to regulate the output voltage of a multi series-connected reconfigurable battery system (e.g., battery pack assembly 202), by dynamically selecting a subset of all available battery cells 772 and dynamically switching them in to (online) or out of (offline) the battery string 766 (aka, cell string or cell string array).

The battery management architecture provides an intelligent processing system that monitors and controls the reconfigurable battery functions. To that end, the battery management architecture includes a battery pack controller 730 operatively coupled to a battery supervisory circuit 732 to enable (online) or bypass (offline) any battery cell 772 in the battery string to adjust the variable output voltage of the reconfigurable battery pack 212 to achieve a commanded output voltage for the battery string. While illustrated using separate blocks and components, the battery pack controller 730 and the battery supervisory circuit 732 may share common circuitry and/or common processors. For example, the battery pack controller 730 and the battery supervisory circuit 732 may be provided as a single system or component.

As will be discussed, the battery management system 700 can use a combination of hardware switching and protection elements, and a software-based cell-selection process based on a number of cell- and pack-level criteria. The hardware instrumentation measures one or more parameters, including battery voltage, battery temperature, battery-string voltage, battery-pack voltage, battery-pack current, battery-pack-assembly voltage, battery-pack-assembly current, battery pressure (e.g., cell-stack pressure), and/or other parameters useful to inform the cell-selection process within the battery management system 700. This information is evaluated by a processor and associated software via the battery pack controller 730 to determine the state of charge (SoC), state of health (SoH), and equivalent resistance of each battery cell 772 in the battery pack 212, which may be updated on a periodic basis.

As noted above, battery management systems that cannot switch battery cells 772 in or out of a battery string 766 are limited by the weakest battery cell 772 in the battery string 766. Such limitations include, for example, battery pack capacity, charge rate (enter balance charge early), and maximum discharge rate (high internal resistance). Using a battery pack controller 730 to implement a reconfigurable architecture via one or more battery switches 762 (e.g., a bi-directional switch) allows for the creation of any combination of battery cells 772 in a battery string 766—up to the maximum number of battery cells 772 in the battery pack 212 of the battery pack assembly 202. Additionally, the reconfigurable architecture provides the ability to regulate the output voltage of the battery pack assembly 202 to within 50% of a battery voltage. An obstacle, however, is that there will need to be excess battery cells 772 in the battery pack assembly 202 to recover from failures or regulate output voltages.

FIG. 7 a illustrates a block diagram of an example battery management system 700 having battery pack assembly 202 in a reconfigurable architecture. The battery management system 700 provides a number of advantages. First, the battery management system 700 provides a modular architecture that can be modular down to the level of an individual battery cell 772. Second, it provides a complete solution to reconfigurable battery protection and management. Third, it allows for the addition and removal of battery cells 772 from a series of a battery string 766, which can be performed to adjust an output voltage to yield a variable output voltage or to bypass a defective battery cell 772. Fourth, it enables isolated power domains (e.g., switchable battery modules 770, battery packs 212, battery pack controller 730, etc.) to enable scalable configurations. Fifth, it offers output regulation without requiring complex voltage conversion circuitry. Finally, it can detect and remove battery cells 772 as they wear out or fail without diminishing overall performance of battery pack 212 or battery pack assembly 202.

The battery pack assembly 202 generally comprises a battery pack controller 730 and a plurality of battery packs 212 (illustrated in FIG. 7 a as six battery packs 212 a, 212 b, 212 c, 212 d, 212 e, and 212 f) connected to one another to define a battery pack string 774, which can serve as a battery pack assembly 202. In operation, the battery pack controller 730 monitors and controls operation of the battery pack string 774, including each of the battery packs 212 and components thereof. The battery pack controller 730 may generate a plurality of system outputs (e.g., instructions, which may be analog or digital) to control operation of the battery pack assembly 202 and/or battery packs 212. For example, the battery pack controller 730 can be configured to generate cell-select commands to insert/bypass individual battery cells within the battery packs 212. The system outputs may be based on two or more system inputs. Example system inputs include, inter alia, individual voltage measurements (e.g., per battery cell 772), individual temperature measurements (e.g., per battery cell 772, which may be measured via temperature sensor 758), current measurements (e.g., through battery string 766), and output voltage measurements of the battery pack assembly 202 (e.g., the measure value of the variable output voltage), which may be measured on each side of the top switch 704. Example system outputs may include, inter alia, battery switch control instructions (e.g., a signal/command), the power to the connected load (e.g., a per battery pack 212 or per battery pack assembly 202 basis), and total voltage (e.g., on a per battery pack 212 or per battery pack assembly 202 basis). In other words, the battery pack controller 730 selectively inserts/bypasses battery cells 772 so that they can be charged, discharged, or bypassed. For example, the battery cells 772 may be selectively bypassed to achieve a desired voltage or to charge/discharge only a select number of battery cells 772 (e.g., depending on the operating mode or conditions).

The battery pack controller 730 also provides over-voltage and under-voltage protection, as well as over-current protection and short-circuit protection. The battery pack assembly 202 may comprise, for example, six battery packs 212 (illustrated as 212 a through 212 f) electrically connected as a string in series; however, the quantity of battery packs 212 in the battery pack assembly 202 may be sized based on the energy storage needs of the application. It is also possible to electrically connect the battery packs 212 in other electrical configurations to achieve a desired voltage and/or capacity (e.g., in parallel, or a combination of series and parallel).

As illustrated, the battery pack controller 730 may comprise a plurality of bus output switches 768, a micro-controller unit (MCU) 708 operatively coupled with a memory device (e.g., RAM, ROM, flash memory, etc.), a precision current sensor 726 to measure the current to/from the string of battery packs 212, a set of input/output (I/O) expander integrated circuits (IC) 776 a, 776 b, and a DC power supply 728 (e.g., +3.3 VDC supply) to supply any power needed to operate the various components of the battery pack controller 730, such as the processors (e.g., MCU 708) and other ICs. Depending on the desired number of connections, the I/O expander ICs 776 a, 776 b may be, for example, a 16-bit expander.

The plurality of bus output switches 768 can be used to couple the battery pack string 774 to the ACSU 302 so that the battery pack string 774 (or portion thereof) can be charged or discharged. The plurality of bus output switches 768 may comprise, for example, a pre-charge switch 702, a top switch 704 (e.g., a main switch), and an ideal diode switch 706. Each of the bus output switches 768 may be arranged electrically in parallel. Voltage and current sensing of the battery bank 224 of the battery pack assembly 202 may be determined at the bus output switches 768. The plurality of bus output switches may be mechanical switches, solid-state switches, or a combination thereof.

The pre-charge switch 702 may be a bi-directional, maximum string voltage blocking, high impedance output contactor. The pre-charge switch 702 electrically connects the plurality of battery packs 212 to the ACSU 302. As illustrated, the pre-charge switch 702 is provided in line with one or more resistors to provide surge suppression and to limit charge current at the end of charge. The pre-charge switch 702 may employ a bidirectional blocking switch element rated to the maximum output of the battery pack assembly 202. Bi-directionality allows the switch to control current flowing into or out of the battery pack assembly 202. The pre-charge switch 702 may have a higher resistance relative to the top switch 704 (e.g., about 10 ohm (Ω) to 30Ω, or about 20Ω). In operation (i.e., when closed), the pre-charge switch 702 limits in-rush or out-rush currents during safe-to-mate bus connections.

The top switch 704 may be a bi-directional, maximum string voltage blocking, low impedance output contactor. The top switch 704 connects the plurality of battery packs 212 directly to the ACSU 302. The top switch 704 may be designed with ultra-low resistance to minimize losses during nominal operation, resulting in a low insertion loss. The top switch 704 may employ a bidirectional blocking switch element rated to the maximum output of the battery pack assembly 202. Bi-directionality allows the top switch 704 to control current flowing into or out of the battery pack assembly 202. The top switch 704 enables the battery packs 212 (e.g., those of the switchable battery modules 770) to use switches with lower blocking voltages.

The ideal diode switch 706 may be a unidirectional, maximum string voltage blocking, low impedance discharge only contactor. The ideal diode switch 706, when enabled, prevents current flow into the plurality of battery packs 212 through top switch 704 via the diode. The ideal diode switch 706 allows only for discharging of the battery pack assembly 202. The ideal diode switch 706 may be typically used when multiple battery pack assemblies 202 are connected in parallel (e.g., to define the battery bank 224).

The MCU 708 controls overall operation of the battery pack assembly 202 in response to commands from, for example, the system controller 216. For example, the MCU 708 may perform battery management and control algorithms to ensure that the battery cells 772 in the system are operating with in safe operating conditions. To that end, the MCU 708 may monitor, inter alia, SoC, SoH, and battery resistance, which can be used to perform sorting and battery balancing. The MCU 708 may be operably coupled with the ACSU 302 over, for example, a controller area network (CAN). The MCU 708 comprises a general purpose (digital) input/output (GPIO) signals, analog-to-digital converter (ADC) 710, a set of CAN interfaces 712, 714 and a plurality of serial peripheral interface (SPI) buses 716, 718, 720, 722, 724. The MCU 708 is communicatively coupled with each of the battery packs 212 via one or more SPI data busses. I/O expander ICs 776 a, 776 b allow for multiple control signals that expand the available I/O to the MCU 708.

FIG. 7 b illustrates a block diagram of an example battery pack 212 (e.g., Detail B of FIG. 7 a , battery pack 212 a) having a battery supervisory circuit 732. Together with the battery pack controller 730, the battery supervisory circuit 732 converts cell-select commands from the battery pack controller 730 to selectively insert/bypass individual battery cells 772 of the battery string 766 within the battery pack 212, while also conditioning and digitizing voltages and temperatures of the individual battery cells. A strain measurement may be included from each battery pack 212 to monitor the compression of the battery cells 772 of each battery pack 212. The battery pack 212 generally comprises a plurality of battery cells 772, and a plurality of battery switches 762 to selectively enable (activated) or bypass one or more of the plurality of battery cells 772 within the battery string 766. The plurality of battery switches 762 may be electrically coupled to the plurality of battery cells 772 via a printed circuit board assembly (PCBA). The battery cells 772 may be provided as single-cell batteries, multi-cell batteries, or a combination thereof. Depending on the desired nominal voltage of a multi-cell battery, for example, the battery cells may be electrically arranged and connected in a series configuration, in a parallel configuration, or a combination thereof to achieve a desired nominal voltage and/or power for the battery cell 772.

In addition to serving as a battery cell interface, the PCBA can serve as a platform for the battery supervisory circuit 732 (or a portion thereof). The battery supervisory circuit 732 generally comprises low voltage circuitry, high voltage circuitry, a plurality of temperature sensors 758, and a plurality of strain sensors 760. The battery pack 212 may comprise a dedicated memory 734 for storing battery cell 772 and PCBA-specific parameters.

A pair of quad-channel digital isolators 778 a, 778 b may be communicatively coupled with the I/O expander ICs 776 a, 776 b of the battery pack controller 730. The pair of quad-channel digital isolators 778 a, 778 b may be used to communicate digital signals from the battery pack controller 730, across a magnetic, optical, or galvanic isolation boundary between the low and high voltage circuitry, to the high voltage side of the circuitry.

An I/O expansion module 740 may be used to communicate data directionally between the battery pack controller 730 (via the quad-channel digital isolator 778 a) and the battery string 766. As illustrated, the battery string 766 generally comprises a plurality of switchable battery modules 770, each switchable battery module 770 having a battery cell 772 and a battery switch 762 associated therewith. As will be described in greater detail below, the switchable battery modules 770 may be electrically arranged in series to define the battery string 766 composed of battery cells 772 that are configured in an active state (e.g., via the battery switches 762).

The I/O expansion module 740 may communicate, for example, switch control signals between the battery pack controller 730 and the battery switches 762 of the switchable battery modules 770 to selectively activate/deactivate the battery cells 772, for example. The I/O expansion module 740 may be, for example a 16-bit I/O expansion module (e.g., one for each of the 16 battery cells 772). A dual channel isolator 748 may be positioned between the I/O expansion module 740 and each of the battery switches 762. In the event of voltage loss at one or more any battery cells 772 voltage (resulting from, for example, a broken battery cell tab/contactor), an auxiliary (AUX) power supply (PS) 750 can be included at each battery pack 212 to ensure the local switching circuit remains powered through the voltage loss event. The auxiliary power supply has an isolated output, so it can be used at every cell location. The auxiliary power supply may also be enabled by the loss of the associated cell voltage.

An isolated power module 736 can be provided to supply power needed to operate the various components (e.g., ICs, such as the memory 734) of the low and high voltages circuits. The isolated power module 736 may be coupled to a reference voltage 738 (e.g., +3.3V), +3.3 VDC (DIG), +5.7 VDC (ANA). The isolated power module 736 may be, for example, an isolated flyback μModule DC/DC converter with low-dropout (LDO) post regulator with an isolation rating of, for example, 725 VDC. The isolated power module 736 may be operable over an input voltage range of 3.1V to 32V with an output voltage range of 2.5V to 13V (set by a single resistor). The isolated power module 736 may also include a linear post regulator whose output voltage is adjustable from 1.2V to 12V as set by a single resistor. A suitable isolated power module 736 includes, for example, the LTM8048, which is available from Linear Technology.

Various parameters of the battery cells 772 may be measured and communicated to the battery pack controller 730 (via the battery supervisory circuit 732) for processing. The parameters may be monitored/measured on a per battery cell 772 basis. Example parameters include, for example, voltage, current, temperature, and compression of the battery cell 772. For example, the plurality of temperature sensors 758 and the plurality of strain sensors 760 can be physically positioned adjacent the battery cell 772 in the battery pack 212 to monitor, respectively, the temperature and strain of each of the battery cells 772. For example, each battery cell 772 may be associated with a temperature sensor 758 and/or a strain sensor 760 to allow the battery supervisory circuit 732 to monitor each of the battery cells 772 individually. In certain aspects, the battery cell 772 may be configured as a 2p cell assembly where a temperature sensor 758 and/or a strain sensor 760 may be positioned between the two p cells. Alternatively, a single strain sensor 760 could be used to monitor the compression of the full battery pack 212.

Measurements from each of the plurality of temperature sensors 758 (e.g., cell temperature) can be communicated to a thermistor conditioning amplifier 754 on the high voltage side, while measurements from the strain sensor(s) 760 (e.g., cell compression) can be communicated to a strain signal amplifier 756 on the high voltage side. The voltage measurements for each battery cell 772 may be provided using a differential amplifier 752, which can function as a voltage sensor, on the high voltage side. In certain aspects, a thermistor conditioning amplifier 754 may be provided for each temperature sensor 758 and a differential amplifier 752 may be provided for each battery cell 772. Therefore, in a battery pack 212 having 16 battery cells 772, 16 thermistor conditioning amplifiers 754 and 16 differential amplifiers 752 may be used. While it is possible to provide a temperature sensor 758 and/or a strain sensor 760 at each battery cell 772, a single temperature sensor 758 and/or a single strain sensor 760 may instead be used for the entire battery cell-stack of a battery pack 212.

The measured parameters from the thermistor conditioning amplifiers 754, the strain signal amplifier(s) 756, and the differential amplifiers 752 may be inputted to one or more multiplexers. In operation, the one or more multiplexers select one of plurality of analog (or digital, if applicable) input signals from the various sensors and forwards the selected input into a single output. The one or more multiplexers may include, for example, a 2:1 multiplexer 744 and a 4:1 multiplexer 746. The output from the 2:1 multiplexer 744 and the 4:1 multiplexer 746 may be inputted to an analog-to-digital (A-D) voltage converter 742. The A-D voltage converter 742 may be, for example, a 16-channel (8-differential) micropower 16-bit ΔΣ analog-to-digital converter. The parameters, now in digital format, may be outputted from the A-D voltage converter 742 and back to the battery pack controller 730 via the quad-channel digital isolator(s) 778 a, 778 b and SPI bus for processing. As can be appreciated, one or more clock (clk) signals may be used to synchronize the components during data/signal processing.

FIG. 7 c illustrates a diagram of an example battery string 766 for use in a battery pack 212. As illustrated, the battery string 766 may comprise a plurality of switchable battery modules 770 arranged in series. Each switchable battery module 770 comprises, for example, a battery cell 772 (e.g., a single battery cell or multiple battery cells, which can be arranged as a cell assembly), a battery switch 762, and a cell selection algorithm function 764. For illustrative purposes, the battery string 766 is illustrated with six switchable battery modules 770; however, additional or fewer switchable battery modules 770 may be used. In operation, one or more desired battery cells 772 can be selected and switched into the battery string 766 via the battery switches 762 such that aggregate string voltage of the battery pack 212 (output voltage) achieves a predetermined target output voltage.

The number of cells per battery cell 772 in a switchable battery module 770 may be adjusted based on the desired level of control granularity of the battery pack 212. In one example (e.g., where a more-granular switching approach is desired), the switchable battery module 770 may comprise a single-cell battery with a single battery cell such that a single battery cell may be added to, or removed from, the battery string 766 one-by-one (i.e., individually). In other words, each battery switch 762 (and associated cell selection algorithm function 764) may be associated with a single battery cell and configured to electrically connect (insert or activate) or electrically disconnect (remove or bypass) the single battery cell from the active battery string 766.

In another example (e.g., where a less-granular switching approach is desired or acceptable), the switchable battery module 770 may comprise a multi-cell battery having multiple battery cells (e.g., two or more, which may be connected electrically to one another in series or in parallel) may be added to, or removed from, the battery string 766 individually. In such an arrangement, the group of battery cells within the battery pack 212 may be associated with a single cell selection algorithm function 764 and a single battery switch 762 such that the battery switch 762 can be selectively actuated to electrically connect or electrically disconnect the group of battery cells from the active battery string 766. Therefore, the number of battery cells to be inserted or bypassed at a time using a single battery switch 762 may be selected based on the needs of the battery system.

In embedded designs, an A-D voltage converter 742 of the battery supervisory circuit 732 at each switchable battery module 770 (e.g., at the one or more battery cells) can serve as the voltage sensor to measure the voltage of the battery cells 772.

Detail C provides an enlargement of an example battery switch 762. The battery switch 762 may provide single pole, double throw (SPDT) switch functionality. Therefore, as illustrated, the battery switch 762 may be a SPDT switch where the pole (1P) can be connected to either the first throw (1T) to bypass the battery cell 772 (shunt switch position 762 a) from the battery string 766 or the second throw (2T) to insert/activate the battery cell 772 (series switch position 762 b) by including it in series with the battery string 766. Each of the plurality of battery switches 762 can use low voltage MOSFETs with low series resistance to improve efficiency, which can be provided in small packages. The battery switch 762 can be implemented with MOSFET, mechanical relays, reed switches, or IGBT switches (or another form of solid-state switch) in a break-before-make (BBM or non-shorting) arrangement, which interrupts one circuit before closing the other, thereby mitigating any risk of shorting the battery cell 772 being switched. For example, the battery switch 762 may be provided using back-to-back FETs (e.g., N-MOSFETS) in common source configuration, TRIACs (a three terminal semiconductor device), bipolar junction transistors (BJT), etc.

Therefore, in one aspect, a reconfigurable battery system, such as the battery pack 212, may include a plurality of switchable battery modules 770, a battery supervisory circuit 732, and a battery pack controller 730. The plurality of switchable battery modules 770 are electrically arranged in series to define a battery string 766 defining an output voltage for the battery pack 212 (e.g., a variable output voltage), each of the plurality of switchable battery modules 770 comprising a battery (e.g., a battery cell 772) and a battery switch 762. Configuring the battery switch 762 in the first position (e.g., series switch position 762 b) electrically places the battery in series with the battery string 766 to increase the output voltage, while configuring the battery switch 762 in the second position (e.g., shunt switch position 762 a) electrically bypasses the battery from the battery string 766. The battery supervisory circuit 732 is operably coupled to each of the plurality of switchable battery modules 770, wherein the battery supervisory circuit 732 is configured to monitor, for each of the plurality of switchable battery modules 770, one or more parameters of the battery. The battery pack controller 730 operably coupled to the battery supervisory circuit 732 to selectively switch, for each of the plurality of switchable battery modules 770, the battery switch 762 between the first position and the second position based at least in part on the one or more parameters of the battery and in accordance with a predetermined switching routine such that the output voltage is substantially equal to a predetermined target output voltage.

Using the example illustrated in FIG. 7 c , certain battery cells 772 may be selectively bypassed based on, for example, their charge state to provide a desired string voltage. For example, if a string voltage of at least 10 volts is needed (a predetermined target output voltage), switchable battery modules 770 1, 3, and 4 may be activated to provide 10.29 volts (i.e., 3.43v+3.19v+3.67v), while the remainder are bypassed. As the voltages of the battery cells 772 of first, third, and fourth switchable battery modules 770 (1, 3, and 4) decrease during the discharge cycle (or increase during a charge cycle), one or more of the second, fifth, and sixth switchable battery modules 770 (2, 5, and 6) may be selectively activated or deactivate (e.g., one by one) to maintain a string voltage of at least 10 volts. Alternatively, a different group of switchable battery modules 770 may be activated to maintain the predetermined target output voltage. Therefore, the battery pack controller 730 may be configured to switch the battery switch 762 of each of the plurality of switchable battery modules 770 individually (i.e., one-by-one) until the predetermined target output voltage is achieved at the variable voltage output.

A battery pack 212 for the solar-powered aircraft 100 a, 100 b may comprise, for example, a battery string 766 with 32 battery cells 772, which may be prismatic, cylindrical, or pouch cells. Therefore, as illustrated, each switchable battery module 770 within the battery pack 212 may employ a cell selection algorithm function 764 and a battery switch 762 to electrically connect or electrically disconnect (bypass) a battery cell 772 from the active battery string 766, thereby adjusting the voltage of the battery string 766 one battery cell 772 at a time. Nominally, about 75% of the battery cells 772 may be active across the battery pack 212 at a given time, where fewer battery cells 772 are active at start of discharge because voltage of the battery cells 772 are higher at that time. As can be appreciated, as the voltage of the battery cells 772 decreases toward the end of discharge, additional battery cells 772 are needed to maintain the programmed voltage. Therefore, the battery pack 212 can be configured and sized such that all available energy is utilized at worst case (longest night) time of year.

All battery pack assemblies 202 in a single battery bank 224 can be programmed simultaneously. To achieve the high bus voltages, each battery pack assembly 202 may employ at least about 100 battery cells 772 and provided a usable voltage of about 2.75V to 4.3V per battery cell 772. Battery pack assemblies 202 of more than 100 battery cells 772 in series are also contemplated for added capacity. Therefore, the battery pack assemblies 202 for the solar-powered aircraft 100 a, 100 b may comprise, for example, 10 to 1,000 battery cells 772, more preferably about 50 to 500 battery cells 772, even more preferably, about 75 to 300 battery cells 772, most preferably, about 100 to 200 battery cells 772. The bus voltage can be set dynamically in response to varying mission and aircraft conditions. For example, the bus voltage of the external bus can be reduced to increase drive system efficiency for night time and low altitude flight, to compensate for line drop when powering remote motors (via boom cross-tie switch(es) 304 a, 304 b) in the event of motor failure, or to implement MPPT.

The internal reconfiguration of the battery cell 772, via the battery supervisory circuit 732 in the battery pack 212, provides: (1) adjustable bus voltage during charge and discharge; (2) tolerance to battery cell failures; (3) lossless cell balancing during charge and discharge; (4) extended latitude reach or life through rest period; and (5) more accurate battery state estimation. For example, the battery pack 212 may employ a plurality of battery switches 762 to provide controlled access to individual battery cells 772 in the battery pack's 212 battery string 766. Generally, the number of active (“online”) battery cells 772 is greater than (or equal to) the maximum bus voltage, divided by the minimum voltage of the battery cells 772. Using this approach, only a subset of battery cells 772 are charged or discharged at a given time, while the other cells are disconnected/rested (bypassed).

Traditional battery packs are vulnerable to even a single battery-cell failure, rendering the battery pack unusable and forfeiting the remaining energy still in the viable (i.e., good/usable) batteries. A programmable voltage architecture, however, provides the ability to bypass a defective battery cell 772 in the battery string 766 in accordance with a predetermined switching routine, thereby resulting in a battery pack 212 that is immune to battery and battery cell failures. Even multi-battery and multi-cell failures do not render the battery string 766 unusable and do not degrade battery pack capacity (except for the availability of the lost battery cells 772 that may be bypassed) until failure count of battery cells 772 accounts for a significant percentage of the total battery count. Such architecture allows for full utilization of the capacity of all viable battery cells in the battery pack 212.

In addition to cell failure, as battery cells age over time (and multiple charge/discharge cycles), the impedance/resistance, and capacity degrade and battery cell characteristics diverge. Premature degradation of even a single battery cell can bring down a traditional pack, resulting in wasted energy trapped in remaining good cells. The battery supervisory circuit 732, however, tracks impedance/resistance and capacity of each battery cell 772 over time. Accordingly, the battery pack 212 can implement preventive measures against cell degradation (or further cell degradation) by balancing the loading across the most viable battery cells. This implementation ensures that, absent an unexpected failure or defect, battery cells are constantly balanced and degrade at equal rate. The battery supervisory circuit 732 can therefore maximizes the capacity of the battery pack 212 (and therefore, the battery pack assembly 202/battery bank 224) over its expected/usable lifetime without dissipating excessive energy in battery cell balancing schemes. Accordingly, all available charge is used, but distributed over a larger population of battery cells.

When the battery cell 772 is out of the battery string 766 (i.e., bypassed), the battery's 772 SoC can be determined by measuring the battery's 772 open circuit voltage (OCV). When the battery cell 772 is in the battery string 766, the battery's 772 SoC can be estimated by measuring the in-and-out-flowing current. One technique for estimating the SoC of a battery cell 772 using the in-and-out-flowing current is known as the coulomb counting method (also known as ampere hour counting and current integration). The coulomb counting method employs battery current readings mathematically integrated over the usage period to calculate SoC values, which can be given by the equation:

${SoC} = {{So{C\left( t_{0}^{} \right)}} + {\frac{1}{C_{r{ated}}^{}}{\int_{t_{0}^{}}^{t_{0}^{} + \tau}{\left( {I_{b}^{} - I_{loss}^{}} \right){dt}}}}}$ where SoC(t₀) is the initial SOC, C_(rated) is the rated capacity, I_(b) is the battery current, and I_(loss) is the current consumed by the loss reactions. The coulomb counting method then calculates the remaining capacity simply by accumulating the charge transferred in or out of the battery.

When a bypassed battery cell 772 is selected and switched into the battery string 766, its internal impedance/resistance can be inferred by measuring the initial drop in cell voltage from the open-circuit (bypassed) to the closed-circuit (enabled or active) condition. Tracking the impedance/resistance of the battery cell 772 over time can be used as part of the SoH estimation to predict when a battery cell 772 is failing at a higher rate than other battery cells 772 in the battery string 766. Battery cell 772 with a higher rate of increasing impedance/resistance could be selected for use less frequently than healthier battery cells 772 (those with lower impedance/resistance) to allow all battery cells 772 to degrade at approximately the same rate and maximize usable lifetime of the complete battery string 766.

To mitigate switch damage during reconfiguration of the battery cells 772 in the battery string 766, a reconfigurable battery system would typically require that each of the switches (e.g., battery switches 762) used to connect the plurality of battery cells 772 accommodate an open circuit voltage (OCV) that is greater than the maximum battery output voltage of the battery pack assembly 202. The physical size and internal resistance of the switch increases as the OCV requirement increases, therefore, the overall size and mass of the entire system would increase due to the larger size of the switching devices. Accordingly, the size and weight of high voltage switch components (e.g., MOSFETs, IGBTs, etc.) needed to realize high voltage reconfigurable battery systems can limit the scalability of the design and energy efficiency of the battery pack 212, battery pack assembly 202, battery bank 224, battery array 200, etc. (losses due to higher resistance of switches). Therefore, while a reconfigurable battery system can overcome the need for additional voltage regulators, they can suffer from added component count and increasing switch size, weight, and dissipated power as battery cell count increases. While small, lightweight, and efficient switch components are available, they are limited in the maximum voltage potential that can be blocked without failure of the switch device.

A switching control method, however, can be implemented with small, lightweight, and efficient switch components such that the battery switches 762 need not block the full voltage potential of the battery string 766. Such a switching control method allows for the use of smaller switch elements for the individual battery cells 772 with one high voltage switch and obviates the need for additional output regulation by not performing reconfigurations when sourcing or sinking power. The switching control method, in effect, provides a high voltage switch through multiple low voltage switches to ensure safe operation of both devices in a switched voltage application. The switching control method offers a number of advantages, including: (1) reduction in size and weight; (2) improved efficiency of switch devices; and (3) prevention of indeterminate states.

The battery pack controller 730 receives data from the battery cells 772 and battery instrumentation systems and actuates the battery switches 762 and bus output switches 768 to reconfigure the cell array string (and hence the battery voltage). In operation, the battery pack controller 730 receives data from the battery and cell instrumentation (voltage, current, temperature, etc.) and intelligently selects a subset of available battery cells 772 to accomplish one of the functions of the reconfigurable battery (output regulation, maximum power point tracking, etc.). The battery pack controller 730 then follows a reconfiguration control method. An example reconfiguration control method 800 is outlined in FIGS. 8 a through 8 c.

The reconfiguration control method 800, which may be implemented by the battery pack controller 730 (or another processor) via software stored to a non-transitory memory device coupled thereto, allows the battery supervisory circuit 732 to reconfigure the battery string 766 for the purposes of, inter alia, balancing battery cell voltage or state-of-charge, changing output voltage, maintaining output voltage regulation, safely bypassing unusable battery cells, controlling current in or out of the battery (e.g., taper charging), and/or maximum power point tracking of a solar array 226. The reconfiguration control method 800 also permits a lower voltage blocking constraint on the battery switches 762 by not applying the full output voltage over any individual battery switch 762. Using this method, the pre-charge switch 702 and top switch 704 can be used to block the maximum battery output voltage, permitting a much lower blocking voltage for individual battery switches 762.

Turning to FIG. 8 a , at the start of the process (step 802), the battery pack 212 is configured with one or more battery cells 772 connected in series (via battery switches 762) and is configured to output a voltage to an electric load 220. At step 804 in the control scheme, the battery pack controller 730 opens an output switch, such as the top switch 704, to disconnect and isolate the battery cells 772 from the external bus (e.g. motor bus, solar panel bus, etc.) and any electric load 220 or solar array 226 coupled thereto. At step 806, the battery pack controller 730 monitors the battery current through the battery string 766 to ensure the output switch is fully disconnected prior to initiating the battery reconfiguration. For example, the battery pack controller 730 can wait until the current through the battery string 766 drops below a predetermined current threshold (subject to the noise of the current sensor) (e.g., 0 mA to 500 mA).

FIG. 8 b describes the process of step 806 in greater detail. At step 824, the battery pack controller 730 calculates the current through the battery string 766 by reading and processing the measurements from one or more sensors (e.g., voltage measurements from voltage sensors via the A-D voltage converter 742).

At step 826, the battery pack controller 730 determines whether the calculated current (from step 824) is less than the predetermined current. If the calculated current is greater than or equal to the predetermined current, then the battery pack controller 730 proceeds to step 828. If the calculated current is less than (i.e., not greater than or equal to) the predetermined current, then the battery pack controller 730 returns at step 832 and proceeds to step 808 of FIG. 8 a.

At step 828, the battery pack controller 730 determines whether a predetermined period of time has elapsed since the battery pack controller 730 calculated the current at step 824. The predetermined period of time may be, for example, about one (1) millisecond (ms) to about five (5) seconds (s), more preferably about 5 ms to about 1 s, or most preferably about 25 ms. To track the predetermined period of time, a timer function may be used. For example, the timer function may be triggered upon calculating the current at step 824 (or entering step 806). If the predetermined period of time has not elapsed at step 828, then the battery pack controller 730 re-calculates the current through the battery string 766 at step 830 by again reading and processing the measurements from one or more sensors. Upon recalculating the current, the process returns to step 826, where the recalculated current is again compared to the predetermined current. If the predetermined period of time has elapsed, then the disconnection is deemed to have failed at step 834 and the battery pack controller 730 returns at step 832 to step 820 of FIG. 8 a.

Turning back to FIG. 8 a , once the current through the battery string 766 drops below the predetermined current, the battery pack controller 730 then reconfigures the battery string 766 array at step 808 by selectively enabling and disabling individual battery switches 762 in accordance with one or more predetermined switch settings. Once the switching process of 808 is complete, the battery pack controller 730 closes the pre-charge switch 702 at step 812.

At step 812, the battery pack controller 730 determines whether the selected battery regulation mode is set to taper charge (i.e., only the pre-charge resistor is used to make the connection to the output). If the regulation mode is set to taper charge, then the process is completed at 818. If the regulation mode is not set to taper charge, then the process proceeds to step 814 where the battery pack controller 730 waits until the pre-charge cycle is complete (passes). If the pre-charge cycle is completed (passes) at step 814, then the process proceeds to step 816. If the pre-charge process is not completed (fails) at step 814, then the process proceeds to step 820.

FIG. 8 c describes the process of step 814 in greater detail. At step 836, the battery pack controller 730 determines (e.g., measures or calculates) the bus voltage (e.g., of local motor bus 324) and battery voltage (e.g., of battery pack assembly 202, such as the output voltage), for example, by reading and processing the measurements from one or more sensors (e.g., voltage measurements from voltage sensors via the A-D voltage converter 742). The battery pack controller 730 then calculates the voltage difference (ΔV) between the bus voltage and battery voltage.

At step 838, the battery pack controller 730 determines whether the calculated voltage difference (from step 836) meets one or more fault conditions. The one or more fault conditions may be, for examples, (A) whether the calculated absolute value voltage difference (from step 836) is greater than a first predetermined voltage (X volts) and (B) whether (1) the rate of change of the absolute value voltage difference is greater than a second predetermined voltage (Y volts) or (2) the absolute value voltage difference is greater than a third predetermined voltage (Z volts, where Z volts is now equal to a pre-charge resistor*current*1.10). If conditions A and B are met at step 838, then the process proceeds to step 840; otherwise the battery pack controller 730 returns at step 848 and proceeds to step 820 of FIG. 8 a . A purpose of step 838 is to ensure that the battery pack assembly 202 coming online substantially matches that of the external bus (e.g., the other battery pack assemblies 202).

By way of example, for a battery pack controller 730 used in connection with the solar-powered aircraft 100 a, 100 b, the first predetermined voltage may be, for example, about 1 volt to about 20 volts, more preferably about 5 volts to about 15 volts, or most preferably about 10 volts. The second predetermined voltage may be, for example, about 1 volt to about 20 volts, more preferably about 2 volts to about 8 volts, or most preferably about 4 volts, while the third predetermined voltage may be, for example, about 25 volt to about 200 volts, more preferably about 50 volts to about 150 volts, or most preferably about 100 volts.

At step 840, the battery pack controller 730 determines whether a predetermined period of time has elapsed since the battery pack controller 730 calculated the voltage difference (ΔV) at step 836. The predetermined period of time may be, for example, about 1 millisecond (ms) to about 5 seconds (s), more preferably about 5 ms to about 1 s, or most preferably about 25 ms. The timer function may be triggered upon calculating the voltage difference at step 836 (or entering step 814). If the predetermined period of time has not elapsed at step 840, then the battery pack controller 730 again reads and processes the measurements from one or more sensors at step 842 and then re-calculates the voltage difference at step 848. Upon recalculating the voltage difference, the process returns to step 838, where the recalculated voltage difference is again compared to conditions A and B. If the predetermined period of time has elapsed at step 840, then the pre-charge process is deemed to have failed at step 846 and the battery pack controller 730 returns at step 848 to step 820 of FIG. 8 a.

At step 816 the battery pack controller 730 actuates the top switch 704, thereby connecting the battery cells 772 to the external bus and electric load 220. Upon actuating the top switch 704, then the process is completed at 818.

At step 820, the process is deemed to have failed and the process is completed at 818. As discussed above, the process is deemed to have failed if either one of steps 806 or 814 fail. If the pre-charge switch 702 had been closed at step 820, then the pre-charge switch 702 is opened (disconnected) at step 822; otherwise, step 822 can be skipped.

While the various solar and battery power systems and methods are generally described in connection with a solar-powered aircraft, they may be applied to virtually any industry where a reconfigurable battery system is desired. In addition, the order or presentation of method steps is not intended to require this order of performing the recited steps unless a particular order is expressly required or otherwise clear from the context. Thus, while particular embodiments have been shown and described, it will be apparent to those skilled in the art that various changes and modifications in form and details may be made therein without departing from the spirit and scope of this disclosure and are intended to form a part of the invention as defined by the following claims, which are to be interpreted in the broadest sense allowable by law. It will be appreciated that the methods and systems described above are set forth by way of example and not of limitation. Numerous variations, additions, omissions, and other modifications will be apparent to one of ordinary skill in the art. 

What is claimed is:
 1. An apparatus for power management of an aircraft, the apparatus comprising: at least one memory; instructions in the apparatus; and processor circuitry to execute the instructions to: in response to a disconnection of a battery string from a load, determine a quantity of current associated with the battery string based on a sensor measurement, the battery string including a plurality of batteries; in response to a determination that the quantity of the current satisfies a threshold, identify ones of the plurality of the batteries to be coupled to the load based on respective charge states of the ones of the plurality of the batteries; control a first switch to pre-charge the ones of the plurality of the batteries; and in response to the pre-charging of the ones of the plurality of the batteries, control a second switch to couple the ones of the plurality of the batteries to at least one of the load or a solar panel, the solar panel to charge the ones of the plurality of the batteries.
 2. The apparatus of claim 1, wherein the threshold is a first threshold, the ones of the plurality of the batteries including a first battery, a second battery, and a third battery, the determination is a first determination, and the processor circuitry is to execute the instructions to: determine a first charge state of the first battery; determine a second charge state of the second battery; determine a third charge state of the third battery; determine whether a sum of at least one of the first charge state, the second charge state, or the third charge state satisfies a second threshold; and in response to a second determination that the sum of the first charge state and the second charge state satisfies the second threshold: control a third switch to couple the first battery to the first switch and the second switch, the third switch coupled to the first battery; control a fourth switch to couple the second battery to the first switch and the second switch, the fourth switch coupled to the second battery; and control a fifth switch to disconnect the third battery from the first switch and the second switch, the fifth switch coupled to the third battery.
 3. The apparatus of claim 1, wherein the threshold is a first threshold, the charge states are first charge states, the determination is a first determination, and the processor circuitry is to execute the instructions to: determine a first voltage associated with a motor of the aircraft, the motor coupled to a propulsor of the aircraft; determine a second voltage based on respective second charge states of the ones of the plurality of the batteries; and in response to a second determination that a difference between the first voltage and the second voltage satisfies a second threshold, identify a fault condition associated with the ones of the plurality of the batteries.
 4. The apparatus of claim 3, wherein the fault condition is a first fault condition, and the processor circuitry is to execute the instructions to: determine a rate of change of the difference; and in response to a third determination that the rate of change satisfies a third threshold and the difference satisfies a fourth threshold: determine whether a time period has elapsed; in response to a fourth determination that the time period has elapsed, identify a second fault condition; and control the first switch to discontinue the pre-charging of the ones of the plurality of the batteries by switching the first switch from a closed position to an open position.
 5. The apparatus of claim 1, wherein the processor circuitry is to execute the instructions to, in response to the determining that the quantity of the current satisfies the threshold and a time period has elapsed: identify a fault condition associated with the disconnecting of the battery string from the load; and control the first switch to halt the pre-charging of the ones of the plurality of the batteries.
 6. The apparatus of claim 1, wherein the processor circuitry is to execute the instructions to, in response to the controlling of the second switch to couple the ones of the plurality of the batteries to the load: identify a fault condition of a first battery of the ones of the plurality of the batteries; control a third switch to bypass the first battery from the load; and control a fourth switch to couple a second battery of the plurality of the batteries to the load, the second battery not included in the ones of the plurality of the batteries.
 7. The apparatus of claim 1, wherein the plurality of the batteries are included in a first battery bank, and the processor circuitry is to execute the instructions to: identify a fault condition of the first battery bank; control a third switch to bypass the first battery bank from the at least one of the load or the solar panel; and control a fourth switch to couple a second battery bank to the load.
 8. The apparatus of claim 1, wherein the processor circuitry is to execute the instructions to, in response to not identifying a fault condition based on the pre-charging the ones of the plurality of the batteries, control the second switch to couple the ones of the plurality of the batteries to the solar panel to charge the ones of the plurality of the batteries.
 9. The apparatus of claim 1, wherein the threshold is a first threshold, the determination is a first determination, and the processor circuitry is to execute the instructions to: control a third switch to couple a first battery of the plurality of the batteries to the load; determine an output voltage provided to the load; and in response to a second determination that the output voltage does not satisfy a second threshold, control a fourth switch to couple a second battery of the plurality of the batteries to the load, the coupling of the second battery to the load to cause the second threshold to be satisfied.
 10. A storage disc or storage device comprising instructions that, when executed, cause processor circuitry to: in response to a disconnection of a battery string from a load, determine a quantity of current associated with the battery string based on a sensor measurement, the battery string including a plurality of batteries; in response to a determination that the quantity of the current satisfies a threshold, identify ones of the plurality of the batteries to be coupled to the load based on respective charge states of the ones of the plurality of the batteries; control a first switch to pre-charge the ones of the plurality of the batteries; and in response to the pre-charging of the ones of the plurality of the batteries, control a second switch to couple the ones of the plurality of the batteries to at least one of the load or a solar panel, the solar panel to charge the ones of the plurality of the batteries.
 11. The storage disc or storage device of claim 10, wherein the threshold is a first threshold, the ones of the plurality of the batteries including a first battery, a second battery, and a third battery, the determination is a first determination, and the instructions, when executed, cause the processor circuitry to: determine a first charge state of the first battery; determine a second charge state of the second battery; determine a third charge state of the third battery; determine whether a sum of at least one of the first charge state, the second charge state, or the third charge state satisfies a second threshold; and in response to a second determination that the sum of the first charge state and the second charge state satisfies the second threshold: control a third switch to couple the first battery to the first switch and the second switch, the third switch coupled to the first battery; control a fourth switch to couple the second battery to the first switch and the second switch, the fourth switch coupled to the second battery; and control a fifth switch to disconnect the third battery from the first switch and the second switch, the fifth switch coupled to the third battery.
 12. The storage disc or storage device of claim 10, wherein the threshold is a first threshold, the charge states are first charge states, the determination is a first determination, and the instructions, when executed, cause the processor circuitry to: determine a first voltage associated with a motor of an aircraft, the motor coupled to a propulsor of the aircraft; determine a second voltage based on respective second charge states of the ones of the plurality of the batteries; and in response to a second determination that a difference between the first voltage and the second voltage satisfies a second threshold, identify a fault condition associated with the ones of the plurality of the batteries.
 13. The storage disc or storage device of claim 12, wherein the fault condition is a first fault condition, and the instructions, when executed, cause the processor circuitry to: determine a rate of change of the difference; and in response to a third determination that the rate of change satisfies a third threshold and the difference satisfies a fourth threshold: determine whether a time period has elapsed; in response to a fourth determination that the time period has elapsed, identify a second fault condition; and control the first switch to discontinue the pre-charging of the ones of the plurality of the batteries by switching the first switch from a closed position to an open position.
 14. The storage disc or storage device of claim 10, wherein the instructions, when executed, cause the processor circuitry to, in response to the determining that the quantity of the current satisfies the threshold and a time period has elapsed: identify a fault condition associated with the disconnecting of the battery string from the load; and control the first switch to halt the pre-charging of the ones of the plurality of the batteries.
 15. The storage disc or storage device of claim 10, wherein the instructions, when executed, cause the processor circuitry to, in response to the controlling of the second switch to couple the ones of the plurality of the batteries to the load: identify a fault condition of a first battery of the ones of the plurality of the batteries; control a third switch to bypass the first battery from the load; and control a fourth switch to couple a second battery of the plurality of the batteries to the load, the second battery not included in the ones of the plurality of the batteries.
 16. A method for power management of an aircraft, the method comprising: in response to disconnecting a battery string from a load, determining a quantity of current associated with the battery string based on a sensor measurement, the battery string including a plurality of batteries; in response to determining that the quantity of the current satisfies a threshold, identifying ones of the plurality of the batteries to be coupled to the load based on respective charge states of the ones of the plurality of the batteries; controlling a first switch to pre-charge the ones of the plurality of the batteries; and in response to the pre-charging of the ones of the plurality of the batteries, controlling a second switch to couple the ones of the plurality of the batteries to at least one of the load or a solar panel, the solar panel to charge the ones of the plurality of the batteries.
 17. The method of claim 16, wherein the sensor measurement is a first voltage measured by a sensor associated with a first battery of the ones of the plurality of the batteries, and further including: converting, with an amplifier coupled to the sensor, the first voltage to a second voltage, the second voltage less than the first voltage; delivering, with a multiplexer coupled to the amplifier, the second voltage to a converter; converting, with the converter, the second voltage to a digital output; and delivering, with a digital isolator coupled to the converter, the digital output to a controller, the controller to determine the quantity of the current based on the digital output.
 18. The method of claim 16, wherein the threshold is a first threshold, the ones of the plurality of the batteries including a first battery, a second battery, and a third battery, and further including: measuring a first charge state of the first battery; measuring a second charge state of the second battery; measuring a third charge state of the third battery; determining whether a sum of at least one of the first charge state, the second charge state, or the third charge state satisfies a second threshold; and in response to determining that the sum of the first charge state and the second charge state satisfies the second threshold: controlling a third switch to couple the first battery to the first switch and the second switch, the third switch coupled to the first battery; controlling a fourth switch to couple the second battery to the first switch and the second switch, the fourth switch coupled to the second battery; and controlling a fifth switch to disconnect the third battery from the first switch and the second switch, the fifth switch coupled to the third battery.
 19. The method of claim 16, wherein the threshold is a first threshold, the charge states are first charge states, and the pre-charging of the ones of the plurality of the batteries includes: determining a first voltage associated with a motor of the aircraft, the motor coupled to a propulsor of the aircraft; determining a second voltage based on respective second charge states of the ones of the plurality of the batteries; and in response to determining that a difference between the first voltage and the second voltage satisfies a second threshold, identifying a fault condition associated with the ones of the plurality of the batteries.
 20. The method of claim 19, wherein the fault condition is a first fault condition, and further including: determining a rate of change of the difference; and in response to determining that the rate of change satisfies a third threshold and the difference satisfies a fourth threshold: determining whether a time period has elapsed; in response to determining that the time period has elapsed, identifying a second fault condition; and controlling the first switch to discontinue the pre-charging of the ones of the plurality of the batteries by switching the first switch from a closed position to an open position. 